GB2167401A - Injection nitration engine - Google Patents

Injection nitration engine Download PDF

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Publication number
GB2167401A
GB2167401A GB08424220A GB8424220A GB2167401A GB 2167401 A GB2167401 A GB 2167401A GB 08424220 A GB08424220 A GB 08424220A GB 8424220 A GB8424220 A GB 8424220A GB 2167401 A GB2167401 A GB 2167401A
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GB
United Kingdom
Prior art keywords
engine
nitration
steam
nitroglycerine
pumps
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
GB08424220A
Inventor
Kevin Maurice Buckley
Original Assignee
Kevin Maurice Buckley
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Kevin Maurice Buckley filed Critical Kevin Maurice Buckley
Priority to GB08424220A priority Critical patent/GB2167401A/en
Publication of GB2167401A publication Critical patent/GB2167401A/en
Withdrawn legal-status Critical Current

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Classifications

    • CCHEMISTRY; METALLURGY
    • C06EXPLOSIVES; MATCHES
    • C06BEXPLOSIVES OR THERMIC COMPOSITIONS; MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES
    • C06B47/00Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase
    • C06B47/02Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase the components comprising a binary propellant
    • C06B47/04Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosives; Suspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase the components comprising a binary propellant a component containing a nitrogen oxide or acid thereof
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02BINTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B45/00Engines characterised by operating on non-liquid fuels other than gas; Plants including such engines
    • F02B45/06Engines characterised by operating on non-liquid fuels other than gas; Plants including such engines operating on fuel containing oxidant
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K9/00Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/425Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants propellants
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00Road transport of goods or passengers
    • Y02T10/10Internal combustion engine [ICE] based vehicles
    • Y02T10/30Use of alternative fuels, e.g. biofuels

Abstract

The formation of nitroglycerine in situ is used to produce a propellant force. Separate supplies of glycerol, nitric acid, and sulphuric acid are fed by appropriate valved supply lines to a chamber, where the materials are mixed, the reaction initiated and the resulting controlled explosion used for propulsion.

Description

SPECIFICATION injection nitration engine This invention relates to nitration engines. Nitration engines are known wherebye nitroglycerine oxidises to produce a propelant.

However nitroglycerine is highly unstable and therefore has to be mixed with some inert substance to stabilise it which makes its oxidisation erratic and dangerouse.

The present invention provides a method of controlled oxidisation of concentrated nitric acid, (concentrated) sulphuric acid and a suitable organic substance. I.E. glycerol. The engine comprises of three separate injectors each carrying one of the substances, producing the required mixed amount of explosive material only in the explosion chamber at the time it is required to explode whether it be periodicaly or continually.

An embodiment of the invention will now be described with reference to the accompanying drawing.

Figure 1 shows a section through the engine with its components.

Figure 2 shows three different mechanisms which the engine is capable of propeling.

Figure 3 shows safety resevoir.

Refering to the drawing the injector pumps provide an accurate measured amount of fluid in unison to the combustion chamber to provide the correct force of explosion.

The three liquids only join and mix inside the combustion chamber.

The engine injectors pumps reserviors are coated in a suitable non corrosive material.

.Reference key to figures 1:- Point of mix and ignition.

2:- Combustion chamber.

3:- Ignitor.

4:- Rocket thrust.

5:- Water safety jackets.

6:- Concentrated sulphuric acid.

7:- Concentrated nitric acid.

8:- Suitable organic material I.E. glycerine.

9:- Casing.

10: Pumps.

11: Engine casing (stainless).

12:- Piston.

14:- Turbine thrust.

15:- Injectors.

16:- Inner reservoir.

The injection nitration engine keeps the different compounds apart, untill they are required to mix and oxidise, in a controlled reaction inside the combustion chamber.

The engine brings the compounds together in the correct proportions and quantities to ensure the required force of explosion at the required moment in time.

The injectors, pumps and pipes allow only a one way flow to the combustion chamber.

The ignitor and pumps start and stop the reaction if required.

The injection nitration engine allows controlled oxidisation of nitro glycerine without mixing it with an inorganic or stabilising compound.

CLAIMS Amendments to the claims have been filed, and have the following effect: The claims above have been deleted or textually amended.

New or textually amended claims have been filed as follows:- It is known to introduce separate oxidisable/oxidising reactant streams into a combustion zone to produce propulsive power.

Usually these oxidisable materials have been developed to be suitable for space rocket propulsion, because of the technical and enviromental problems, low temperatures and high altitudes they prove to be uneconomic or unsuitable as a means of producing electrical energy.

The injection nitration engine is a stationary engine designed to drive a turbine or piston via rocket propulsion (see drawing) as an economic aiternative to a steam turbine.

When steam is expanded adiabatically through a stationary nozzle it does not retain all the heat it originally had.

The heat reieased during expansion, of course, does not disappear. According to the first law of thermodynamics it must reappear as work energy in equivalent amounts (778 foot pounds for each BTU).

In the case of steam expanding through a stationary nozzle the moving steam must gain this mechanical energy with the result that its speed is increased.

An ordinary expansion involving a heat prop of about 100 B.T.U.S. Of steam has the capacity to increase its speed to the large magnitude of 30 miles/minute.

This gives some clue as to the reason why so light a fluid medium as steam is capable of producing so much power in a machine of moderate dimensions.

When nitroglycerine oxidises it expands 1,500 times in volume which gives it the capacity to increase its speed to the very large magnitude of 360 miles/minute.

This also gives some clue as to the reason why nitroglycerine is capable of producing so much power in a machine of small dimensions.

The cost of the commercial ingredients which go to make nitroglycerine are comparable with other fuels (coal, gas, oil and nuclear) but are renewable and capable of producing far greater power.

Therefore it's economically better at producing electrical energy via turbine (piston) drive.

**WARNING** end of DESC field may overlap start of CLMS **.

Claims (1)

  1. **WARNING** start of CLMS field may overlap end of DESC **.
    SPECIFICATION injection nitration engine This invention relates to nitration engines. Nitration engines are known wherebye nitroglycerine oxidises to produce a propelant.
    However nitroglycerine is highly unstable and therefore has to be mixed with some inert substance to stabilise it which makes its oxidisation erratic and dangerouse.
    The present invention provides a method of controlled oxidisation of concentrated nitric acid, (concentrated) sulphuric acid and a suitable organic substance. I.E. glycerol. The engine comprises of three separate injectors each carrying one of the substances, producing the required mixed amount of explosive material only in the explosion chamber at the time it is required to explode whether it be periodicaly or continually.
    An embodiment of the invention will now be described with reference to the accompanying drawing.
    Figure 1 shows a section through the engine with its components.
    Figure 2 shows three different mechanisms which the engine is capable of propeling.
    Figure 3 shows safety resevoir.
    Refering to the drawing the injector pumps provide an accurate measured amount of fluid in unison to the combustion chamber to provide the correct force of explosion.
    The three liquids only join and mix inside the combustion chamber.
    The engine injectors pumps reserviors are coated in a suitable non corrosive material.
    .Reference key to figures 1:- Point of mix and ignition.
    2:- Combustion chamber.
    3:- Ignitor.
    4:- Rocket thrust.
    5:- Water safety jackets.
    6:- Concentrated sulphuric acid.
    7:- Concentrated nitric acid.
    8:- Suitable organic material I.E. glycerine.
    9:- Casing.
    10: Pumps.
    11: Engine casing (stainless).
    12:- Piston.
    14:- Turbine thrust.
    15:- Injectors.
    16:- Inner reservoir.
    The injection nitration engine keeps the different compounds apart, untill they are required to mix and oxidise, in a controlled reaction inside the combustion chamber.
    The engine brings the compounds together in the correct proportions and quantities to ensure the required force of explosion at the required moment in time.
    The injectors, pumps and pipes allow only a one way flow to the combustion chamber.
    The ignitor and pumps start and stop the reaction if required.
    The injection nitration engine allows controlled oxidisation of nitro glycerine without mixing it with an inorganic or stabilising compound.
    CLAIMS Amendments to the claims have been filed, and have the following effect: The claims above have been deleted or textually amended.
    New or textually amended claims have been filed as follows:- It is known to introduce separate oxidisable/oxidising reactant streams into a combustion zone to produce propulsive power.
    Usually these oxidisable materials have been developed to be suitable for space rocket propulsion, because of the technical and enviromental problems, low temperatures and high altitudes they prove to be uneconomic or unsuitable as a means of producing electrical energy.
    The injection nitration engine is a stationary engine designed to drive a turbine or piston via rocket propulsion (see drawing) as an economic aiternative to a steam turbine.
    When steam is expanded adiabatically through a stationary nozzle it does not retain all the heat it originally had.
    The heat reieased during expansion, of course, does not disappear. According to the first law of thermodynamics it must reappear as work energy in equivalent amounts (778 foot pounds for each BTU).
    In the case of steam expanding through a stationary nozzle the moving steam must gain this mechanical energy with the result that its speed is increased.
    An ordinary expansion involving a heat prop of about 100 B.T.U.S. Of steam has the capacity to increase its speed to the large magnitude of 30 miles/minute.
    This gives some clue as to the reason why so light a fluid medium as steam is capable of producing so much power in a machine of moderate dimensions.
    When nitroglycerine oxidises it expands 1,500 times in volume which gives it the capacity to increase its speed to the very large magnitude of 360 miles/minute.
    This also gives some clue as to the reason why nitroglycerine is capable of producing so much power in a machine of small dimensions.
    The cost of the commercial ingredients which go to make nitroglycerine are comparable with other fuels (coal, gas, oil and nuclear) but are renewable and capable of producing far greater power.
    Therefore it's economically better at producing electrical energy via turbine (piston) drive.
GB08424220A 1984-09-25 1984-09-25 Injection nitration engine Withdrawn GB2167401A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB08424220A GB2167401A (en) 1984-09-25 1984-09-25 Injection nitration engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB08424220A GB2167401A (en) 1984-09-25 1984-09-25 Injection nitration engine

Publications (1)

Publication Number Publication Date
GB2167401A true GB2167401A (en) 1986-05-29

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
GB08424220A Withdrawn GB2167401A (en) 1984-09-25 1984-09-25 Injection nitration engine

Country Status (1)

Country Link
GB (1) GB2167401A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1995026467A2 (en) * 1994-03-29 1995-10-05 Igor Urban Bipropellant rocket motor
ES2200687A1 (en) * 2002-05-08 2004-03-01 Tavares Justo Salgado Nitroglycerin electrical central. (Machine-translation by Google Translate, not legally binding)

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB653409A (en) * 1946-01-10 1951-05-16 Borg Warner Self-sufficient fuel
GB761070A (en) * 1953-08-28 1956-11-07 California Research Corp Propellant composition
GB770162A (en) * 1953-08-28 1957-03-20 California Research Corp Propellant
GB771807A (en) * 1952-12-10 1957-04-03 California Research Corp Oxidizing agent
GB804590A (en) * 1953-07-06 1958-11-19 Phillips Petroleum Co Improvements in propellants
GB806870A (en) * 1953-08-28 1958-12-31 California Research Corp Propellant fuel
GB816769A (en) * 1956-03-19 1959-07-15 California Research Corp Hypergolic fuel containing mercaptals or mercaptols
GB831103A (en) * 1957-07-13 1960-03-23 Werner Heyl Propellant for rockets and other jet engines
GB1184602A (en) * 1966-07-22 1970-03-18 Degussa Process for Desensitising Reactions.

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB653409A (en) * 1946-01-10 1951-05-16 Borg Warner Self-sufficient fuel
GB771807A (en) * 1952-12-10 1957-04-03 California Research Corp Oxidizing agent
GB804590A (en) * 1953-07-06 1958-11-19 Phillips Petroleum Co Improvements in propellants
GB761070A (en) * 1953-08-28 1956-11-07 California Research Corp Propellant composition
GB770162A (en) * 1953-08-28 1957-03-20 California Research Corp Propellant
GB806870A (en) * 1953-08-28 1958-12-31 California Research Corp Propellant fuel
GB816769A (en) * 1956-03-19 1959-07-15 California Research Corp Hypergolic fuel containing mercaptals or mercaptols
GB831103A (en) * 1957-07-13 1960-03-23 Werner Heyl Propellant for rockets and other jet engines
GB1184602A (en) * 1966-07-22 1970-03-18 Degussa Process for Desensitising Reactions.

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
S FORDHAM }HIGH EXPLOSIVES AND PROPELLANTS} (1966) PAGE 42 TO 43 *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1995026467A2 (en) * 1994-03-29 1995-10-05 Igor Urban Bipropellant rocket motor
WO1995026467A3 (en) * 1994-03-29 1995-11-09 Igor Urban Bipropellant rocket motor
ES2200687A1 (en) * 2002-05-08 2004-03-01 Tavares Justo Salgado Nitroglycerin electrical central. (Machine-translation by Google Translate, not legally binding)

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WAP Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1)